Abstract: A reduction in excitation amplitudes affecting turbine blade durability in a turbine nozzle assembly having a plurality of vanes and turbine blades, includes: identifying a turbine blade design of the turbine nozzle assembly; performing a modal model analysis of at least one of the turbine blades in the turbine blade design; reducing aerodynamic impact by ensuring that each of the turbine blades is free of aero-excitation from an upstream flow at the vanes in an operating speed range; identifying blade natural frequencies with respect to the nozzle vanes; and modifying a trailing edge of at least one of the vanes to reduce the excitation amplitudes.

Abstract: A system and method of inducing proper operation of a diesel engine exhaust after-treatment system employing SCR technology monitors components to detect a fault condition representing one of a DEF level fault, a DEF quality fault, and a tampering fault, activates a trigger event indicator in response to detecting the fault condition. The trigger event indicator provides an indicium to an operator of the presence of the fault condition. The system and method also activates an inducement event indicator in response to activating the trigger event indicator. The inducement event indicator provides an indicium to the operator that the engine will be shut down if the fault condition is not addressed within a predetermined time period. The system and method causes shutdown of the engine when the fault condition is not addressed within the predetermined time period.

Abstract: The present disclosure provides a subsonic rotor and/or stator blade profile of an axial turbomachine compressor, such as a turbojet. The blade comprises a leading edge with an S-shaped lateral profile in its mid-plane. Specifically, the profile includes, from its inner end to the outer end, a first convex portion including the foremost point of the blade, and a second concave portion including the rearmost area of the blade. This profile enables the fluid flow between 20% and 80% of the blade's length to be redistributed. This so-called “sweep” profile increases the performance of the stage with such blades because it reduces blade tip vortex losses as well as secondary losses.

Abstract: A gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, an airfoil having a tip wall that joins outer spanwise ends of a suction sidewall and a pressure sidewall, a tip leakage control channel recessed into an outer surface of the tip wall, a tip leakage control vane integrally formed on the tip wall adjacent to the tip leakage control channel and an air seal radially outward of the tip wall and positioned to minimize leakage at the tip wall.

Abstract: Methods and systems are provided for exhaust heat recovery and hydrocarbon trapping at an exhaust bypass assembly. Exhaust gas may flow in both directions through an exhaust bypass passage and each of a HC trap and a heat exchanger coupled to the bypass passage. The HC trap may be purged with the hot exhaust and heat from the exhaust may be recovered at the heat exchanger.

Abstract: The object is to simplify systems in a solar thermal power generation plant and thereby provide a solar thermal power generation system achieving reduction in the construction cost and the power generation cost.

Abstract: A ventilation fan housing includes: a shield body having a receiving space, a maintenance opening and a wire-positioning opening adjacent to the maintenance opening, with the maintenance opening and wire-positioning opening penetrating a wall of the shield body and communicating with the receiving space, and with a lid connecting with the shield body detachably to cover the maintenance opening.

Abstract: The invention concerns a device for recirculation of exhaust gases from an engine (1) of a motor vehicle, comprising a first exhaust gas recirculation line (9) called an EGR line, a first heat exchanger (10) provided on said EGR line (9) to ensure cooling of the recirculated exhaust gases, and treatment means (11) for the exhaust gases allowing limitation of the pH of the condensate arising from said gases. The treatment means (11) are provided upstream of the first exchanger (10) along the path of the exhaust gases, and the exchanger (10) comprises a heat exchanger bundle made of aluminum and/or aluminum alloy.

Abstract: A gas turbine engine is provided that includes a core flow path to direct a core stream flow. A common flow path is outboard of the core flow path, where the common flow path directs both a second stream flow and a third stream flow. Another gas turbine engine is provided that includes an outer case structure around a central longitudinal engine axis. An intermediate case structure is inboard of the outer case structure, where the intermediate case structure and the outer case structure direct both a third stream flow and a second stream flow. An inner case structure is inboard of the intermediate case structure, where the inner case structure and the intermediate case structure direct a core stream flow.

Abstract: A gas turbine engine includes a thrust reverser including a plurality of blocker doors moveable between a deployed position and a stowed position. A gap is defined between adjacent blocker doors when in the stowed position. A plurality of divots are mounted forward of the plurality of blocker doors to substantially cover the gap between the adjacent blocker doors when in the stowed position.

Abstract: A pitch bearing assembly for a wind turbine may include an outer race and an inner race rotatable relative to the outer race. The inner race may define an inner circumference and may include a plurality of gear teeth around the inner circumference. The inner race may also include a circumferential flange extending at least partially around the inner circumference. In addition, the pitch bearing assembly may include a stiffener coupled to the circumferential flange.

Abstract: An airfoil according to an exemplary aspect of the present disclosure includes, among other things, a suction sidewall and a pressure sidewall, each sidewall extending spanwise from an airfoil base and extending chordwise between a leading edge and a trailing edge. A tip wall extends chordwise from the leading edge to the trailing edge and joining respective outer spanwise ends of the suction and pressure sidewalls. A tip leakage control channel is recessed into the tip wall, the tip leakage control channel including a control channel floor that extends between a first control channel vane sidewall and a second control channel vane sidewall established by a corresponding tip leakage control vane. An internal cooling cavity is disposed between the suction sidewall and the pressure sidewall and a channel cooling aperture feeds airflow from the internal cooling cavity to the tip leakage control channel.

Abstract: The impeller is provided with: a disc section equipped with a tube section, the grip section of which is fixed by thermal deformation to a rotation shaft that is rotated around the axis line, and a main disc body, which is provided on the other end in the axial direction from the grip section and which extends outward in the radial direction of the rotation shaft; and blade sections that protrude from the main disc body in the axial direction. The disc section is provided with a hoop stress-limiting section, the tube section of which extends further towards the other end in the axial direction than the main disc body.

Abstract: A method for assembling a variable geometry turbomachine with a bearing housing, an adjacent turbine housing, a turbine wheel rotating in the turbine housing about a turbine axis; an inlet passage upstream of the turbine wheel between inlet surfaces of first and second wall members, one wall member moveable along the turbine axis to vary the inlet passage size; vanes across the inlet passage connected to a first wall member; an array of vane slots defined by the second wall member to receive the vanes for relative movement between the wall members; the second wall member comprising a shroud defining vane slots; the second wall member supported by a support member retained by a mounting feature; the mounting feature being one of the bearing housings, the turbine housing, or the actuation element; and the shroud is fixed to the support member.

Abstract: A gas turbine engine blade (22), including an airfoil substrate (10) having an exterior surface, wherein: a base (14) of the airfoil substrate is located at a 0% radial on an inner platform surface (20) and a tip (16) of the airfoil substrate is located at a 100% radial; wherein at the 0% radial a cross-sectional profile of the exterior surface is substantially characterized by nominal X and Y coordinates present in Table 1; and wherein at a 50% radial location a cross-sectional profile of the exterior surface is characterized by nominal X and Y coordinates present in Table 6.

Abstract: An internal combustion engine includes a cylinder block defining first and second cylinders, and a cylinder head coupled to the block. The engine also includes a passage having a first outlet and a second outlet for exhausting post-combustion gasses from the cylinder head. The engine additionally includes a mechanism for selectively activating and deactivating the first cylinder and a turbocharging system having a low-flow turbocharger and a high-flow turbocharger. The low-flow turbocharger is driven by gasses from the first outlet and the high-flow turbocharger is driven by gasses from the second outlet. The turbocharging system also includes a first flow-control device that directs the gasses via the first and second outlets to the turbochargers when the first and second cylinders are activated. The first flow-control device also directs the gasses via the first outlet only to the low-flow turbocharger and blocks the second outlet when the first cylinder is deactivated.

Abstract: A method for fan speed control for a condenser fan in an air conditioning system includes determining a refrigerant condition at an inlet of a compressor by a condenser fan speed control module; determining a refrigerant condition at an outlet of the compressor by the condenser fan speed control module; determining a parabolic curve of a relationship between an air conditioning system performance metric and a speed of the condenser fan based on the determined inlet condition and the determined outlet condition by the condenser fan speed control module; identifying an optimum condenser fan speed based on a vertex of the parabolic curve by the condenser fan speed control module; and controlling the speed of the condenser fan to meet the optimum fan speed by the condenser fan speed control module.

Abstract: There is provided a steam power cycle system in which steam power cycles using pure materials as a working fluid is used in a multiple stage to reduce pressure loss in the flow channels in the respective heat exchanger so that the fluid serving as heat sources has been caused to make an effective heat exchange with the working fluid. More specifically, not only that the respective flow channels for the fluid serving as heat sources in the evaporator and the condenser in the respective steam power cycle units are connected in series to each other, but the evaporator and the condenser comprise a cross-flow type heat exchanger and are arranged respectively in a flowing direction of the fluid serving as heat source. Consequently, it is possible to reduce the length of the flow channels to the minimum necessary, simplify the flow channel structure, and reduce the pressure loss.

Abstract: A rotor for a wind/water power machine that can reduce fluid resistance. A rotor provided with a hub and blades. A projected plane perpendicular to a rotational center axis line of the rotor, front edges of the blades protrude, in at least one part, forward in the rotational direction of the rotor relative to a first line segment; front edge protruding tips thereof are disposed in positions separated outward in the radial direction of the rotor from the outer peripheral edge of the hub by a length 0.4 to 0.6 times the length of the blade; and portions of the front edges of the blades that extend from the ends on the inside in the radial direction of the rotor to the front edge protruding tips are curved or bent convexly, in at least one part, rearward in the rotational direction of the rotor relative to a second line segment.

Abstract: An improved system, apparatus and method for controlling vane angles in a gas turbine engine, and more specifically, for correcting vane angle error in a gas turbine engine. An active synchronization ring comprises a plurality of micro-actuators coupled to the synchronization ring to correct distortion in the synchronization ring. The micro-actuators apply a bending moment to the synchronization ring to cancel or compensate for synchronization ring distortion. The micro-actuators may be controlled open loop or closed loop. Strain sensors measure ring distortion and provide signals to the controller for closed loop control.